An inner platform structure of a stator vane for a gas turbine engine includes a male circumferential side opposite a female circumferential side, the male circumferential side includes a male wall received at least partially within a female wall of a neighboring stator vane at an interface with a pad at the interface.
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1. An inner platform structure of a stator vane for a gas turbine engine, the inner platform structure comprising:
a female circumferential side that forms a portion of a female box structure having at least one female wall;
a male circumferential side opposite said female circumferential side, said male circumferential side forms a portion of a male box structure having at least one male wall that is receivable at least partially within a female box structure of a neighboring stator vane at an interface; and
a pad at said interface, said pad expands in response to an increase in temperature to an operational temperature above a nominal room temperature to close a gap at said interface at said nominal room temperature.
9. A stator vane for a gas turbine engine, comprising:
an airfoil between an outer platform structure and an inner platform structure, said inner platform structure includes a female circumferential side and a male circumferential side that forms a portion of a box structure, said male circumferential side includes a multiple of male walls that are received at least partially within at least one female wall of a neighboring stator vane at an interface; and
a pad on each of either said multiple of male walls or said at least one female wall at said interface, wherein at a nominal room temperature, the interface provides a respective gap between said pad and an opposed wall surface, said pad expands in response to an increase in temperature above said nominal room temperature to close said gap.
11. A stationary vane ring assembly, comprising:
a first stator vane inner platform structure, said first stator vane inner platform structure including a first stator vane female circumferential side and a first stator vane male circumferential side that forms a portion of a first stator vane box structure;
a second stator vane inner platform structure, said second stator vane inner platform structure including a second stator vane female circumferential side and a second stator vane male circumferential side that forms a portion of a second stator vane box structure, said second stator vane inner platform structure nests at least partially within said first stator vane inner platform structure at an interface between said first stator vane box structure and said second stator vane box structure, said first stator vane male circumferential side includes a multiple of male walls that are received at least partially with a multiple of female walls of a neighboring stator vane; and
a multiple of pads at said interface, at least one pad of said multiple of pads on each of either said multiple of male walls or said multiple of female walls at said interface, wherein at a nominal room temperature, the interface provides a respective gap between said at least one pad and an opposed wall surface to permit disassembly, wherein said at least one pad expands in response to an increase in temperature above said nominal room temperature to close said gap.
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This application claims the benefit of provisional application Ser. No. 62/066,998, filed Oct. 22, 2014.
This disclosure was made with Government support under N00019-02-C-3003 awarded by The United States Navy. The Government has certain rights in this disclosure.
The present disclosure relates to components for a gas turbine engine and, more particularly, to a vane ring assembly therefor.
Gas turbine engines, such as those that power modern commercial and military aircraft, generally include a compressor section to pressurize an airflow, a combustor section to burn a hydrocarbon fuel in the presence of the pressurized air, and a turbine section to extract energy from the resultant combustion gases.
The compressor section includes a case circumscribing an engine axis with axially alternating vane rings and rotor disks. Each vane ring may be constructed of multiple vane clusters distributed circumferentially about the interior of the case. One type of vane cluster utilizes a stator two-pack (doublet), with an outer platform structure and an inner box structure. The inner box structure of neighboring stator two-packs nest together during assembly utilizing a swage joint. Due to tolerances and gapping required to permit assembly, this swage joint may have some “play” such that each stator may locally deflect before the swage joint cross-corners engage during engine operation.
An inner platform structure of a stator vane for a gas turbine engine, the inner platform structure according to one disclosed non-limiting embodiment of the present disclosure includes a female circumferential side. A male circumferential side is opposite the female circumferential side, and includes at least one male wall received at least partially within at least one female wall of a neighboring stator vane at an interface. A pad located at the interface.
A further embodiment of the present disclosure includes, wherein the pad is located on the at least one male wall.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is located on each of a multiple of male walls.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is located on the at least one female walls.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is located on each of a multiple of female walls.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is manufactured of an elastomeric material.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad expands in response to a change in temperature.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the male circumferential side and the female circumferential side form a portion of a box structure.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the male circumferential side corresponds to the female circumferential side.
A further embodiment of any of the foregoing embodiments of the present disclosure includes wherein the male circumferential side and the female circumferential side form a portion of a box structure of an inner platform structure.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the male circumferential side and the female circumferential side form a portion of a box structure of the inner platform structure.
A stator vane for a gas turbine engine according to another disclosed non-limiting embodiment of the present disclosure includes an airfoil between an outer platform structure and an inner platform structure, the inner platform structure includes a female circumferential side and a male circumferential side that forms a portion of a box structure, the male circumferential side includes a multiple of male walls that are received at least partially within at least one female wall of a neighboring stator vane at an interface and a pad at the interface.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is located on at least one of the multiple of male walls.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is located on at least one of the multiple of female walls.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the pad is manufactured of an elastomeric material.
A stationary vane ring assembly according to one disclosed non-limiting embodiment of the present disclosure includes a first stator vane inner platform structure, the first stator vane inner platform structure including a female circumferential side and a male circumferential side that forms a portion of a box structure; a second stator vane inner platform structure, the second stator vane inner platform structure including a female circumferential side and a male circumferential side that forms a portion of a box structure, the second inner platform structure nests at least partially within the first stator vane inner platform structure at an interface; and a multiple of pads at the interface.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein each of the multiple of pads form a respective gap at a nominal temperature.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein each of the multiple of gaps are closed at an engine operating temperature.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein the multiple of pads are manufactured of an elastomeric material.
A further embodiment of any of the foregoing embodiments of the present disclosure includes, wherein each of the multiple of pads are located on at least one of a male wall and a female wall at the interface.
The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be exemplary in nature and non-limiting.
Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiments. The drawings that accompany the detailed description can be briefly described as follows:
An outer case structure 36 and an inner case structure 38 define a generally annular secondary airflow path 40 around a core airflow path 42. Various structures may define the outer case structure 36 and the inner case structure 38 which essentially define an exoskeleton to support rotational hardware therein. Air that enters the fan section 22 is divided between core airflow through the core airflow path 42, and secondary airflow through the secondary airflow path 40. The core airflow passes through the combustor section 26, the turbine section 28, then the augmentor section 30, where fuel may be selectively injected and burned to generate additional thrust through the nozzle system 34.
The secondary airflow may be utilized for a multiple of purposes to include, for example, cooling, pressurization and variable cycle operations. The secondary airflow as defined herein is any airflow different from the core airflow. The secondary airflow may ultimately be at least partially injected into the core airflow path 42 adjacent to the duct section 32 and the nozzle system 34. It should be appreciated that additional airflow streams, such as a third stream airflow of variable cycle engine architectures, may additionally be provided.
With reference to
With reference to
With reference to
In this disclosed non-limiting embodiment, the female circumferential side 80 includes a first female wall 84, a second female wall 86, a third female wall 88, and a fourth female wall 90, while the male circumferential side 82 includes a corresponding first male wall 92, a second male wall 94, a third male wall 96, and a fourth male wall 98 (
The male walls 92, 94, 96, 98 each includes a respective pad 100, 102, 104, 106. Each pad 100, 102, 104, 106 is formed of an elastomeric material to include, but not be limited to silicone rubber. Each pad 100, 102, 104, 106 may be formed as a coating, applique or other application to the substrate which is typically a nickel super alloy, ceramic matrix composite, or other relatively high temperature material appropriate to the particular engine section.
Each pad 100, 102, 104, 106 is respectively located on the outer male walls 92, 94, 96, 98 opposite the female walls 84, 86, 88, 90 (shown), the inner surface of the female walls 84, 86, 88, 90 opposite the outer male walls 92, 94, 96, 98, or both. The pads 100, 102, 104, 106 are thereby located between the respective male circumferential side 82 within the female circumferential side 80 to form a swage—type interface 110 (
With reference to
At operating temperatures, when the gap 112 has been sealed due to the expanded pads 100, 102, 104, 106, potential leak passages for secondary flow through the inner box geometry of the inner platform structure 70 are closed, thereby further benefiting engine performance and efficiency. The pads 100, 102, 104, 106, also dampen engine vibrations at the inner box of the stationary vane ring assembly 60.
After the engine 20 is shut down and cools, the pads 100, 102, 104, 106 shrink, again facilitating ease of disassembly, and maintenance thereof.
The use of the terms “a,” “an,” “the,” and similar references in the context of description (especially in the context of the following claims) are to be construed to cover both the singular and the plural, unless otherwise indicated herein or specifically contradicted by context. The modifier “about” used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (e.g., it includes the degree of error associated with measurement of the particular quantity). All ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other. It should be appreciated that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to normal operational attitude and should not be considered otherwise limiting.
Although the different non-limiting embodiments have specific illustrated components, the embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from any of the non-limiting embodiments in combination with features or components from any of the other non-limiting embodiments.
It should be appreciated that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be appreciated that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom.
Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present disclosure.
The foregoing description is exemplary rather than defined by the limitations within. Various non-limiting embodiments are disclosed herein, however, one of ordinary skill in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. It is therefore to be understood that within the scope of the appended claims, the disclosure may be practiced other than as specifically described. For that reason the appended claims should be studied to determine true scope and content.
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